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A Model of the Flow over Swept Wings with Shock Induced Separation

  • Conference paper
Turbulent Shear-Layer/Shock-Wave Interactions

Part of the book series: International Union of Theoretical and Applied Mechanics ((MANUTECH))

Summary

A new flow model is proposed for describing quasi two-dimensional flows with shock-induced separation on wings of modest sweep. Correlations of the main features of the flow model over a wide range of Reynolds number have been deduced from wind-tunnel tests on wings and aerofoils. These correlations have successfully been used as a basis for simulating ‘full-scale’ flows over wings in the wind tunnel.

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References

  1. Fluid Dynamics of Aircraft Stalling. AGARD CP-102 1972.

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  3. Green, J.E.; A discussion of viscous-inviscid interactions at transonic speeds. Paper 2. AGARD CP-35 1971.

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  4. Fulker, J.L.; Ashill, P.R.; A study of factors influencing shock-induced separation. RAE Technical Report to be published.

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  5. Smith, P.D.; A calculation method for the turbulent boundary layer on an infinite yawed wing in compressible, adiabatic flow. RAE Technical Report 72193 1972.

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Author information

Authors and Affiliations

  1. Royal Aircraft Establishment, Bedford, UK

    J. L. Fulker & P. R. Ashill

Authors
  1. J. L. Fulker
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  2. P. R. Ashill
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Editor information

Editors and Affiliations

  1. Direction de L’Aérodynamique, ONERA, B.P. 72, 29. Av. de la Division Leclerc, F-92322, Châtillon Cedex, France

    J. Délery

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© 1986 Springer-Verlag Berlin, Heidelberg

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Fulker, J.L., Ashill, P.R. (1986). A Model of the Flow over Swept Wings with Shock Induced Separation. In: Délery, J. (eds) Turbulent Shear-Layer/Shock-Wave Interactions. International Union of Theoretical and Applied Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-82770-9_19

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  • DOI: https://doi.org/10.1007/978-3-642-82770-9_19

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-642-82772-3

  • Online ISBN: 978-3-642-82770-9

  • eBook Packages: Springer Book Archive

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